CN102353314A - Detection method for outline of main blade of helicopter - Google Patents
Detection method for outline of main blade of helicopter Download PDFInfo
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- CN102353314A CN102353314A CN2011101540253A CN201110154025A CN102353314A CN 102353314 A CN102353314 A CN 102353314A CN 2011101540253 A CN2011101540253 A CN 2011101540253A CN 201110154025 A CN201110154025 A CN 201110154025A CN 102353314 A CN102353314 A CN 102353314A
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- main blade
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- top airfoil
- strong point
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Abstract
The invention relates to a detection method for an outline of a main blade of a helicopter. According to the method, four supporting points are utilized as basic starting points; an outline difference between an actual blade and a theoretical blade is detected; and then detection is gradually carried out from the leading edge of the main blade and gaps that are recorded every 10 mms and are used for recording an actual blade outline and an outline detection tool are recorded. Compared with the prior art, the technology employed in the invention enables the method has the following characteristics that: the design ides is novel and the detection method can be operated simply; and repeatability of detection results can be ensured.
Description
Technical field
The present invention is a kind of helicopter master blade method for detecting shape, belongs to field of measuring technique.
Background technology
Rotor blade be have aerodynamic configuration, the transverse section is the straight strip structural member of aerofoil profile, complex geometry.Because blade is to the strict demand of aerodynamic configuration, the compound substance rotor blade selects to adopt close die hot-press solidifying forming technology, reaches designing requirement to guarantee blade aerofoil profile precision, torsion angle and surfaceness.In order to improve the pneumatic efficiency of blade, require blade adopt advanced aerofoil profile, blade profile error little, have certain roughness, the distortion of the profile under local aerodynamic loading effect little.Blade adopts the close die hot-press solidifying to be shaped.Close die is made up of upper die and lower die, and cavity mold surface guarantees the aerodynamic configuration requirement of blade in strict conformity with design.In the hot-press solidifying forming process, pressure applies the profile that makes the blade profile strictly meet die cavity internally, reaches the accuracy requirement of blade twist angle, surfaceness and blade aerofoil profile.The quality of blade aeroperformance depends on aerofoil profile.The working environment that rotor blade is special requires the blade aerofoil profile should satisfy the requirement of retreating blade workspace (low mach, big Cy value), satisfies advancing blade workspace (high Mach number, little Cy value) again, and the requirement of floating state.Detect frock, feasible detection method so study reliable profile, to different blade aerofoil profiles excessively and the plane alteration of form all be crucial to helicopter rotor blade.Before, though drawing has clear and definite geometric shape inspection requirements, breathe out and fly to never have feasible profile detection frock and reliable detection method.
Summary of the invention
The present invention designs to the deficiency that exists in the above-mentioned prior art just a kind of helicopter master blade method for detecting shape is provided, and its objective is that the profile that is used for various compound substance helicopter master blades detects.
The objective of the invention is to realize through following technical scheme:
This kind helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
(1) the detection frock that is made up of upper and lower two parts is installed on main blade; The interior profile of frock is the theoretical profile of main blade; The Support Position that the interior profile of frock is provided with on the outer mold surface of four strong points and main blade coincide; These four strong points are respectively the strong point and the preceding strong points of lower aerofoil behind the strong point before the strong point behind the top airfoil, the top airfoil, the lower aerofoil; The leading edge of frock is concordant with " 0-0 " section of main blade, and spacing as the leading edge of frock;
(2) four strong points of adjustment and the upper and lower aerofoil of main blade contacts; The strong point contacts with main blade lower aerofoil with the preceding strong point of lower aerofoil fully after guaranteeing lower aerofoil; Observe the space of the preceding strong point of top airfoil and main blade top airfoil; If the space is mild slit; Detection method is pressed a scheme and is carried out; If the space is significantly to cave in, detection method is carried out by sequence number b scheme;
(3) if the space of the preceding strong point of top airfoil and main blade top airfoil is mild slit, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point of top airfoil and main blade top airfoil, read accumulating values A1 and calculate mean value X;
3.2 use the gap of the preceding strong point of clearance gauge adjustment top airfoil and main blade back, the preceding strong point of lower aerofoil and main blade lower surface to be respectively X, the locking clamp;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade; And lay at its profile position place and the consistent detection clamp of the theoretical profile of main blade; Leading edge with main blade is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D
N＞2mm promptly is recorded as-D
N, if D
N≤2mm promptly is recorded as D
N
(4) if the space of the preceding strong point of top airfoil and main blade top airfoil is significantly to cave in, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size of the top airfoil of the preceding master of the strong point place blade of top airfoil, directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade; And lay at its profile position place and the consistent detection clamp of the theoretical profile of main blade; Leading edge with main blade is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D
N
Above-mentioned four REF1000, REF5120, REF5860, REF6262.5 section are the positions that requires detection in the design; Detect clamp and also should have four; Its external form is the theoretical profile of section, and detecting the clamp surface has scale mark accurately, and the data of carrying out the relevant position when aspect detects read.Through detecting the difference that clamp can reflect mold pressing blade and theoretical profile intuitively.The profile of main blade is the curved surface that radian is arranged, and the profile of detection frock also is a curved surface, has just limited employed testing tool, can not be common clearance gauge commonly used, and can only be bar-shaped, such as feeler gauge.
Four support sections and blade aerofoil profile match;
The advantage of technical scheme of the present invention is that the frock mentality of designing is clear and definite, and detection method is simple to operate, can guarantee the repeatability of testing result, can directly reflect the geometric shape of composite material blade on the data.
Description of drawings
Fig. 1 detects the synoptic diagram of frock for profile of the present invention
Embodiment
Below with reference to accompanying drawing and embodiment technical scheme of the present invention is done to describe in detail further:
This kind helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
(1) the detection frock 2 that is made up of upper and lower two parts is installed on main blade 1; The interior profile of frock 2 is the theoretical profile of main blade 1; The Support Position that the interior profile of frock 2 is provided with on the outer mold surface of four strong points and main blade 1 coincide; These four strong points are respectively the strong point 5 and the preceding strong points 6 of lower aerofoil behind the strong point 4 before the strong point 3 behind the top airfoil, the top airfoil, the lower aerofoil; The leading edge of frock 2 is concordant with " 0-0 " section of main blade 1, and spacing as the leading edge of frock;
(2) four strong points of adjustment and main blade 1 upper and lower aerofoil contacts; The strong point 5 contacts with main blade 1 lower aerofoil with the preceding strong point 6 of lower aerofoil fully after guaranteeing lower aerofoil; Observe the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil; If the space is mild slit; Detection method is pressed a scheme and is carried out; If the space is significantly to cave in, detection method is carried out by sequence number b scheme;
(3) if the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil is mild slit, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil, read accumulating values A1 and calculate mean value X;
3.2 the strong point 4 is respectively X, the locking clamp with main blade 1 upper surface, the preceding strong point 6 of lower aerofoil with the gap of main blade 1 lower surface before using clearance gauge adjustment top airfoil;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade 1; And lay and the consistent detection clamp of main blade 1 theoretical profile at its profile position place; Leading edge with main blade 1 is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade 1 begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade 1 and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D
N＞2mm promptly is recorded as-D
N, if D
N≤2mm promptly is recorded as D
N
(4) if the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil is significantly to cave in, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size of the top airfoil of the preceding strong point 4 master of the place blades 1 of top airfoil, directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade 1; And lay and the consistent detection clamp of main blade 1 theoretical profile at its profile position place; Leading edge with main blade 1 is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade 1 begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade 1 and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D
N
Compared with prior art, mentality of designing of the present invention is novel, and detection method is simple to operate, can guarantee the repeatability of testing result.
Claims (1)
1. helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
(1) going up of main blade (1) the detection frock (2) that is made up of upper and lower two parts is installed; The interior profile of frock (2) is the theoretical profile of main blade (1); The Support Position that the interior profile of frock (2) is provided with on the outer mold surface of four strong points and main blade (1) coincide; These four strong points are respectively the strong point (5) and the preceding strong points (6) of lower aerofoil behind the strong point (4) before the strong point (3) behind the top airfoil, the top airfoil, the lower aerofoil; The leading edge of frock (2) is concordant with " 0-0 " section of main blade (1), and spacing as the leading edge of frock;
(2) four strong points of adjustment and main blade (1) upper and lower aerofoil contacts; The strong point (5) contacts with main blade (1) lower aerofoil with the preceding strong point (6) of lower aerofoil fully after guaranteeing lower aerofoil; Observe the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil; If the space is mild slit; Detection method is pressed a scheme and is carried out; If the space is significantly to cave in, detection method is carried out by sequence number b scheme;
(3) if the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil is mild slit, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil, read accumulating values A1 and calculate mean value X;
3.2 the strong point (4) is respectively X, the locking clamp with main blade (1) upper surface, the preceding strong point (6) of lower aerofoil with the gap of main blade (1) lower surface before using clearance gauge adjustment top airfoil;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section in main blade (1); And lay and the consistent detection clamp of the theoretical profile of main blade (1) at its profile position place; Leading edge with main blade (1) is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade (1) begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade (1) and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D
N＞2mm promptly is recorded as-D
N, if D
N≤2mm promptly is recorded as D
N
(4) if the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil is significantly to cave in, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size that the preceding strong point (4) of top airfoil is located the top airfoil of main blade (1), directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section in main blade (1); And lay and the consistent detection clamp of the theoretical profile of main blade (1) at its profile position place; Leading edge with main blade (1) is spacing; Adjust the accurate angle that detects clamp; Confirm to detect " 0 " scale mark position of illustrating on the clamp; Leading edge from main blade (1) begins again, along tangential every interval 10mm, uses columned feeler gauge to write down the distance value D between main blade (1) and the detection clamp profile
N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D
N
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101540253A CN102353314B (en) | 2011-06-10 | 2011-06-10 | Detection method for outline of main blade of helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101540253A CN102353314B (en) | 2011-06-10 | 2011-06-10 | Detection method for outline of main blade of helicopter |
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| CN102353314A true CN102353314A (en) | 2012-02-15 |
| CN102353314B CN102353314B (en) | 2013-08-07 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104669153A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Blade torsional angle measurement fixture and method |
| CN105157658A (en) * | 2015-09-06 | 2015-12-16 | 中国商用飞机有限责任公司 | Contour detection apparatus of airplane skin |
| CN105252768A (en) * | 2015-09-14 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Verifying cover plate and verifying method used for formation of special-shaped composite material foam interlayer workpiece |
| CN105783751A (en) * | 2014-12-17 | 2016-07-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for testing supporting point vector deformation under multi-field coupling |
| CN105953681A (en) * | 2016-06-18 | 2016-09-21 | 无锡市翱宇特新科技发展有限公司 | Rail supporting bench mold detection apparatus |
| CN108151618A (en) * | 2016-12-06 | 2018-06-12 | 江西昌河航空工业有限公司 | A kind of fixture being detected to foamed material part |
| CN109443139A (en) * | 2018-12-07 | 2019-03-08 | 南通虹波机械有限公司 | The pod line style method of inspection |
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| CN201795764U (en) * | 2010-08-12 | 2011-04-13 | 四川省自贡市海川实业有限公司 | Special measuring tool for radial inclined surface of blade basin |
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Patent Citations (4)
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| US4875777A (en) * | 1987-09-30 | 1989-10-24 | Industrial Technology Institute | Off-axis high accuracy structured light profiler |
| CN1058739A (en) * | 1990-08-07 | 1992-02-19 | 宫哲圣 | Propeller line skeleton moulding method |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104669153A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Blade torsional angle measurement fixture and method |
| CN105783751A (en) * | 2014-12-17 | 2016-07-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for testing supporting point vector deformation under multi-field coupling |
| CN105783751B (en) * | 2014-12-17 | 2018-12-18 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of multi- scenarios method state lower fulcrum vector deformation test method |
| CN105157658A (en) * | 2015-09-06 | 2015-12-16 | 中国商用飞机有限责任公司 | Contour detection apparatus of airplane skin |
| CN105157658B (en) * | 2015-09-06 | 2018-05-01 | 中国商用飞机有限责任公司 | Aircraft skin appearance detection apparatus |
| CN105252768A (en) * | 2015-09-14 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Verifying cover plate and verifying method used for formation of special-shaped composite material foam interlayer workpiece |
| CN105252768B (en) * | 2015-09-14 | 2017-06-27 | 沈阳飞机工业（集团）有限公司 | A kind of verification cover plate and method of calibration for the shaping of special-shaped composite foam layer product |
| CN105953681A (en) * | 2016-06-18 | 2016-09-21 | 无锡市翱宇特新科技发展有限公司 | Rail supporting bench mold detection apparatus |
| CN108151618A (en) * | 2016-12-06 | 2018-06-12 | 江西昌河航空工业有限公司 | A kind of fixture being detected to foamed material part |
| CN109443139A (en) * | 2018-12-07 | 2019-03-08 | 南通虹波机械有限公司 | The pod line style method of inspection |
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|---|---|
| CN102353314B (en) | 2013-08-07 |
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Owner name: HAFEI AVIATION INDUSTRY CO., LTD. Free format text: FORMER OWNER: HARBIN AIRCRAFT INDUSTRIAL (GROUP) CO., LTD. Effective date: 20140424 |
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Effective date of registration: 20140424 Address after: 150066 Heilongjiang city of Harbin province Harbin Pingfang District Youxie Street No. 15 Patentee after: Hafei aviation industry Limited by Share Ltd Address before: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd. |
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